|Publication number||US3901028 A|
|Publication date||Aug 26, 1975|
|Filing date||May 21, 1974|
|Priority date||Sep 13, 1972|
|Publication number||US 3901028 A, US 3901028A, US-A-3901028, US3901028 A, US3901028A|
|Inventors||Leingang John L|
|Original Assignee||Us Air Force|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (8), Referenced by (36), Classifications (8)|
|External Links: USPTO, USPTO Assignment, Espacenet|
United States Patent [191 Leingang 1 Aug. 26, 1975 1 RAMJET WITH INTEGRATED ROCKET BOOST MOTOR  Inventor:
 Assignee: The United States of America as represented by the Secretary of the Air Force, Washington, DC.
 Filed: May 21,1974
[2i] App]. No.2 471,930
Related U.S. Application Data  Continuation-impart of Scr. No, 288,816, Sept, 13,
John L. Leingang, Dayton, Ohio 3,045,517 6/1962 Ryden ct :11. 60/270 S 3,063,240 11/1962 Ledwith 60/225 3,086,359 4/1963 Davis 60/225 3,279,187 10/1966 Lindman 60/245 3,316,716 5/1967 Escher 60/225 3,336,753 8/1967 Mullen et a1", 60/225 3,724,216 4/1973 Smith 60/270 S Primary Examiner-C. J. Husar Assistant Examiner-Robert E. Garrett Attorney, Agent, or Firm-Joseph E. Rusz; Richard J. Killoren l 57 l ABSTRACT A combination rocket motor ramjet engine having the rocket motor located in the ramjet inlet diffuser. All or part of the rocket portion of the apparatus remaining after rocket booster burnout are ejected by air pressure in the diffuser inlet to permit the diffuser to supply ram air for the ramjet engine.
3 Claims, 8 Drawing Figures s OPP! RAMJET W'ITI-I INTEGRATED ROCKET BOOST MOTOR RIGHTS OF THE GOVERNMENT DETAILED DESCRIPTION OF THE INVENTION The invention described herein may be manufacj engine wherein a rocket motor boost fuel grain tured and used by or for the Government of the United States for all governmental purposes without the payment of any royalty.
CROSS REFERENCE TO RELATED APPLICATION This is a continuation-in-part of application Ser. No. 288,816, filed Sept. 13, 1972, now abandoned.
BACKGROUND OF THE INVENTION Various arrangements have been used in combination rocket-ramjet engines. In prior art integral rocketramjet engines, the boost propellant is structurally and functionally integrated with the ramjet combustor as in the Patent to Schubert, No. 3,535,881. In other systems, rocket engines are specially designed to fit in the combustor portion of the ramjet engine. For some applications for combination rocket motor ramjet engines, compact construction is desirable. One such combination rocket motor ramjet engine of compact construction is the type which uses a long inlet diffuser duct extending along the side of the missile to supply air to a sudden expansion or dump type combustor positioned aft of the missile. In these combustors, the rocket boost propellant is located in the combustor. After rocket motor burnout, the apparatus converts to ramjet operation. Fuel is supplied just upstream of the sudden expansion region and a wake region is formed just downstream of the sudden expansion to provide rapid mixing and intense combustion in a short length which permits a compact packaging system.
BRIEF SUMMARY OF THE INVENTION In the combination rocket motor ramjet engine using the dump type combustor, the elongated inlet duct is unused during the rocket phase of the operation. According to this invention, the ramjet inlet diffuser for a sudden expansion type combination rocket motor ramjet engine is designed to contain the rocket boost motor. All or part of the rocket motor apparatus is ejected after rocket motor burnout to permit the inlet diffuser to be used to provide ram air for the ramjet combustor.
IN THE DRAWINGS FIG. 1 of the drawing shows a prior art combination rocket motor ramjet engine with a dump type combustor for the ramjet engine.
FIG. 2 is a front end view of a combination rocketramjet boost motor according to the invention.
FIG. 3 is a partially schematic sectional view of the device of FIG. 2 along the line 3-3.
FIG. 4 is an end view of a thrust frame for the device of FIG. 2.
FIG. 5, shows a schematic sectional view of one type of retainer pin for use in the device of FIG. 2.
FIG. 6 is a partially schematic sectional view of the device of FIG. 2 with the rocket boost motor removed.
FIG. 7 is a schematic view of another embodiment of the invention.
FIG. 8 is a schematic view of a further embodiment of the invention.
is positioned within the combustion 12. Ram air is supplied to the combustor through an inlet diffuser duct 14. Fuel is supplied to the combustor at 15 just upstream of the sudden expansion region 16. The ramjet fuel is normally ignited with a pyrophonic material. In the device of this invention, an integrated boost motor missile 17 is provided with two inlet diffusers 18 for conventional dump type ramjet combustors 19, one of which is shown in FIG. 2, each containing a conventional rocket boost motor 20. The inlet diffusers 18 are designed to hold the rocket motors 20. Each diffuser has a thrust frame 21 secured to the inlet diffuser body in front of rocket motors 20 to take the thrust load. The frames 21 have openings 22, as shown in FIG. 4, to permit air flow to the ramjets 19 after rocket motors 20 are removed from the inlet diffusers 18. The rocket motors 20 are retained in the diffusers by means of break pins 23 of a material such as stainless steel which are threaded into the nozzle wall as shown in FIG. 5. These pins are made strong enough to retain the rocket motors within the diffuser housings during normal handling. During operation of the thrust motors 20, the rocket force is against the thrust frames 21 and the pins 23 take no load. When the rocket motors shut down at about Mach 2, the blast pressure against the front of the rockets in the diffuser inlets 24 breaks the pins 23 and ejects the rocket motor casings from the diffuser chambers.
The ramjet configuration is then as shown in FIG. 6. The ramjet operation is started by supplying fuel from fuel supply 27 to manifold 29 and through holes 30 into chamber 32 through a conventional fuel control 34. The ramjet fuel is ignited in a conventional manner, for example by means of a pyrophoric material, such as tiethylboron, from pressure, bottle 36 supplied to the combustion chamber through inlets 37. The device then operates as a conventional dump type combustor to provide a thrust from nozzle 39. A layer of thermal insulation 38 such as silica phenolic or silicone rubber, is provided on the wall of the ramjet combustion chamber. A conventional warhead and guidance system, shown schematically at 40, is positioned forward of the fuel supply 27.
In the operation of the apparatus, initially the rocket boost motor which may be of current conventional design is ignited in the conventional manner to launch and boost the missile 17. At about Mach-2, or any other design speed, when the boost rockets 20 burn out, the blast air pressure in inlets 24 breaks pins 23 and ejects the rocket motor casings from the inlet diffusers 18. The fuel control then supplies fuel to the combustion chambers through holes 30. The fuel control also supplies pyrophoric material through inlets 37 to ignite the fuel so that the apparatus continues operation as a conventional dump type ramjet engine.
While the device described makes use of a conventional rocket boost motor, the device may be modified, as shown in FIG. 7, with a separate boost chamber formed as a diffuser inlet for a separate ramjet combustor.
In this device, the rocket propellant is located in a rocket casing 50 with the front end 52 designed as a diffuser inlet. A frangible boost motor dome 54 is secured in the front end of the casing 50. The dome may be a serrated glass plate which is shattered by blast air and which passes out through the outlet nozzle 56 after rocket burnout. Other means could be provided for shattering the dome 54, such as an explosive charge or a spring loaded striker.
The closure member 61 is then blown from the position shown to a position against a stop 59 by means of conventional explosive release mechanism 60 to open a passage 66 into combustor chamber 58 for ram air and to seal nozzle 56. A latch 57, in the form of an interference fit, may be provided adjacent stop 59.
After the nozzle 56 is sealed, air from the inlet diffuser passes into a conventional ramjet combustor 58 which is started in a conventional manner and operation as a ramjet continues as described above.
The device of FIG. 7 can be modified for use with the ramjet combustor of FIG. 6, as shown in FIG. 8. In this device, the rocket boost motor is the same as in FIG. '7, but has an ejectable rear portion 65 of the motor casing 50' located in the ramjet combustor chamber 62. In this device, a release mechanism 64 is operated upon burnout by a signal from the fuel control and blast air against wall 67 ejects the motor casing portion 65 from the combustor chamber. The mechanism 64 may be a conventional flange joint held together with explosive bolts. The ramjet is then operated as in the device of FIG. 6.
There is thus provided a combination rocket and ramjet engine with increased packaging efficiency over prior art devices.
1. A combination rocket-ramjet booster, comprising: a missile housing inclosing a payload; at least one dump type ramjet combustor attached to the aft end of said missile housing and having a portion extending into the afi portion of the missile body to form a sudden expansion region; an elongated inlet diffuser duct attached to and extending forward of said combustor over one half the length of the missile housing for supplying ram air to said combustor; means, within said housing for supplying ramjet fuel to said combustor; means for igniting said ramjet fuel in said combustor; a rocket boost motor positioned within said combustor and the inlet difiuser duct; break away means responsive to ram air, in the diffuser inlet, for converting the inlet diffuser duct for ramjet operation after rocket motor burnout.
2. The device, as recited in claim 1, wherein said means for converting the inlet diffuser for ramjet operation includes a rocket motor casing within the combustor and inlet diffuser which is ejectable by ram air after rocket burnout; said rocket motor filling the diffuser cross section and having an exit nozzle positioned within the exhaust nozzle of the ramjet combustor; a thrust frame secured to the inlet diffuser for taking the thrust load of the rocket motor; said thrust frame being forward of and separate from said rocket motor; said breakaway means being a plurality of pins positioned adjacent the ah end of said rocket motor for retaining the rocket motor within the diffuser before launch and being breakable by blast air against the front end of the rocket motor, after rocket motor burnout, to permit ejection of the rocket motor and the conversion of the inlet diffuser duct for ramjet operation.
3. The device as recited in claim 1, wherein the means for converting the inlet diffuser for ramjet operation includes a rocket boost motor dome within the inlet diffuser for sealing the diffuser inlet during rocket boost operation and breakable by ram air upon rocket burnout and an ejectable rocket motor case portion in the ramjet chamber; means for releasing the rocket motor case portion after rocket motor burnout.
i i t
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2644396 *||Oct 1, 1948||Jul 7, 1953||United Aircraft Corp||Aerial missile|
|US3045517 *||May 29, 1957||Jul 24, 1962||Westinghouse Electric Corp||Strip thickness control apparatus|
|US3063240 *||Aug 22, 1960||Nov 13, 1962||United Aircraft Corp||Booster means for a ramjetrocket device|
|US3086359 *||Jul 19, 1960||Apr 23, 1963||James Davis Edward||Integral nozzle separator for a multistage reaction motor|
|US3279187 *||Dec 9, 1963||Oct 18, 1966||Morris W Lindman||Rocket-ramjet propulsion engine|
|US3316716 *||Jul 1, 1964||May 2, 1967||Escher William J D||Composite powerplant and shroud therefor|
|US3336753 *||Sep 28, 1965||Aug 22, 1967||Texaco Experiment Inc||Propulsion devices|
|US3724216 *||Jun 13, 1957||Apr 3, 1973||Us Navy||Combined rocket-ram-jet aircraft|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US4028886 *||Oct 23, 1975||Jun 14, 1977||Mcdonnell Douglas Corporation||Passive chamber wall fragmenter|
|US4391094 *||Jan 16, 1981||Jul 5, 1983||Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung||Destructable air inlet cover for rocket engines|
|US4441312 *||Jun 22, 1979||Apr 10, 1984||The United States Of America As Represented By The Secretary Of The Air Force||Combined cycle ramjet engine|
|US4577542 *||Mar 7, 1984||Mar 25, 1986||The United States Of America As Represented By The Secretary Of The Air Force||Dome restraint assembly for rocket motors|
|US4631154 *||Dec 6, 1985||Dec 23, 1986||The United States Of America As Represented By The Secretary Of The Air Force||Method of constructing a dome restraint assembly for rocket motors|
|US4753169 *||Dec 23, 1985||Jun 28, 1988||General Dynamics, Pomona Division||Ablating electromagnetic shield sheath|
|US5853143 *||Dec 23, 1996||Dec 29, 1998||Boeing North American, Inc.||Airbreathing propulsion assisted flight vehicle|
|US5904319 *||Aug 28, 1997||May 18, 1999||Daimler-Benz Aerospace Ag||Guided missile with ram jet drive|
|US6293091 *||Apr 22, 1999||Sep 25, 2001||Trw Inc.||Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet|
|US6557339 *||Aug 9, 2001||May 6, 2003||Aerospatiale Matra Missiles||Blanking-cap system for an orifice of a conduit, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet|
|US6631610||Jul 5, 1983||Oct 14, 2003||The United States Of America As Represented By The Secretary Of The Air Force||Consumable port cover for ducted integral rocket-ramjet engine|
|US6725664 *||Jan 10, 2002||Apr 27, 2004||Aerospatiale Matra Missiles||Shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet|
|US6907724 *||Feb 6, 2003||Jun 21, 2005||The Boeing Company||Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance|
|US6968695 *||Feb 6, 2003||Nov 29, 2005||The Boeing Company||Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance|
|US7137255||Mar 31, 2005||Nov 21, 2006||United Technologies Corporation||Compact swirl augmented afterburners for gas turbine engines|
|US7168236||Mar 31, 2005||Jan 30, 2007||United Technologies Corporation||Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance|
|US7328571 *||Nov 29, 2004||Feb 12, 2008||United Technologies Corporation||Semi-axisymmetric scramjet flowpath with conformal nozzle|
|US7690192||May 22, 2007||Apr 6, 2010||Pratt & Whitney Rocketdyne, Inc.||Compact, high performance swirl combustion rocket engine|
|US7762058||Apr 17, 2007||Jul 27, 2010||Pratt & Whitney Rocketdyne, Inc.||Ultra-compact, high performance aerovortical rocket thruster|
|US7762077||Dec 5, 2006||Jul 27, 2010||Pratt & Whitney Rocketdyne, Inc.||Single-stage hypersonic vehicle featuring advanced swirl combustion|
|US8256203 *||Jan 28, 2008||Sep 4, 2012||The University Of Alabama In Huntsville||Rocket based combined cycle propulsion unit having external rocket thrusters|
|US20040050062 *||Jan 10, 2002||Mar 18, 2004||Laurent Carton||Shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet|
|US20040050063 *||Feb 6, 2003||Mar 18, 2004||Schmotolocha Stephen N.||Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance|
|US20050081508 *||Feb 6, 2003||Apr 21, 2005||Edelman Raymond B.||Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance|
|US20050178104 *||Mar 31, 2005||Aug 18, 2005||Schmotolocha Stephen N.|
|US20060112674 *||Nov 29, 2004||Jun 1, 2006||United Technologies Corporation||Semi-axisymmetric scramjet flowpath with conformal nozzle|
|US20060230764 *||Mar 31, 2005||Oct 19, 2006||Schmotolocha Stephen N||Compact swirl augmented afterburners for gas turbine engines|
|US20080128547 *||Dec 5, 2006||Jun 5, 2008||Pratt & Whitney Rocketdyne, Inc.||Two-stage hypersonic vehicle featuring advanced swirl combustion|
|US20080256924 *||Apr 17, 2007||Oct 23, 2008||Pratt & Whitney Rocketdyne, Inc.||Ultra-compact, high performance aerovortical rocket thruster|
|US20080256925 *||May 22, 2007||Oct 23, 2008||Pratt & Whitney Rocketdyne, Inc.||Compact, high performance swirl combustion rocket engine|
|US20080283677 *||Dec 5, 2006||Nov 20, 2008||Pratt & Whitney Rocketdyne, Inc.||Single-stage hypersonic vehicle featuring advanced swirl combustion|
|US20140331682 *||Nov 1, 2013||Nov 13, 2014||Mark Bovankovich||High-speed-launch ramjet booster|
|USRE43731 *||Aug 30, 2010||Oct 16, 2012||Aerojet-General||Integrated air inlet system for multi-propulsion aircraft engines|
|DE3002977A1 *||Jan 29, 1980||Jul 30, 1981||Messerschmitt Boelkow Blohm||Deckel aus leicht zerstoerbarem material zum verschliessen der in die brennkammer, insbesondere von staustrahl-raketentriebwerken einmuendenden lufteinlaufoeffnungen, und schlagvorrichtung zum zerstoeren dieses deckels|
|DE3003004A1 *||Jan 29, 1980||Jul 30, 1981||Messerschmitt Boelkow Blohm||Deckel aus leicht zerstoerbarem material zum verschliessen der in die brennkammer, insbesondere von staustrahl-raketentriebwerken einmuendenden lufteinlaufoeffnungen, und schlagvorrichtung zum zerstoeren dieses deckels|
|DE3242585A1 *||Nov 18, 1982||May 24, 1984||Messerschmitt Boelkow Blohm||Device for removing the plug from the air intake ducts opening into the combustion chamber of ram jet engines|
|U.S. Classification||60/225, 60/245, 60/769, 60/263|
|International Classification||F02K7/00, F02K7/18|